Subwavelength Aperture Monopulse Conformal Antenna

ABSTRACT

In various aspects and embodiments, incident electromagnetic radiation is received through a subwavelength aperture in a lens, the subwavelength aperture being defined by a substrate encased in a dielectric medium.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention pertains to remote sensing, and, moreparticularly, to a monopulse antenna employing a subwavelength aperturefor use in missile guidance.

2. Description of the Related Art

Many types of guided airborne systems have historically usedhemispherical radomes at their front end. The hemispherical shape waschosen to accommodate certain physical characteristics in the operationof the guidance systems. While increasing the performance of theguidance systems, they sometimes hampered the overall performance of theairborne system. One significant drawback to hemispherical radomes isthat they create high levels of drag, which inhibit the speed of theairborne system. This is particularly undesirable in a military contextbecause it renders the airborne system more vulnerable to enemy fire,thereby decreasing its survivability, and reduces its lethality.

Efforts therefore have been directed at developing new techniques thatwould accommodate the use of sleek, low drag radomes fostering speedierairborne systems. One technique developed as a part of this effort wasnon-coherent Fresnel direction finding (“NCFDF”). See, e.g., U.S. Pat.No. 6,851,645, entitled “Non-Coherent Fresnel Direction Finding Methodand Apparatus”, issued Feb. 9, 2005, to Lockheed Martin Corporation asassignee of the inventors Brett A. Williams, et al. (“the '645 patent”).This technique ably accommodates the use of sleek radomes. The '645patent is hereby incorporated be reference for its teachings regardingNCFDF as if expressly set forth herein verbatim.

At the same time, some in the art have been pushing to decrease the sizeof such systems to obtain smaller, smarter, guided airborne systems.Desires for smaller guided projectiles, for instance, have producedpressure on sensors to fit within ever smaller dimensions. Opportunitiesfor what may be termed “micro-missiles” such as darts or bullet-likeprojectiles in the neighborhood of 0.25″ diameters, or less, increasethese strenuous demands still further.

NCFDF begins to suffer for miniature missiles due to shrinkingreal-estate available for its window apertures and their associatedlengths. The NCFDF apparatus in the '645 patent, for instance, uses awindow/light-pipe design. The walls of the light-pipe are curved,reducing light rejection compared to straight walls. The aperture of thewindow collects light over its surface while the pipe simply guideslight to its exit by multiple reflections. No focused, phase-frontsensitive optics is required and wall reflection is most efficacious fortotal internal reflection without reflective coatings.

Light rejection and window field-of-view depend on a relation betweenaperture and light pipe length—that is, the aperture must beproportional to that length to avoid ever increasing reflection angleswithin the light-pipe until ultimately they are rejected back out tofree space. If length limits are imposed, thus reducing allowableaperture dimensions, then additional apertures can be added which cansatisfy the length relation for a smaller aperture/multi-windowapproach, increasing aperture area by the number of added windows. Yetmicro-missiles have virtually no length allowance and even spaciousairframes may have existing components conflicting with light-pipeplacement.

The problem is to provide a surface conformal antenna on a sleek radometo allow kinematic range and lethality due both to speed and a clearedcentral axis for lethality enhancer placement. In addition the antennamust provide sufficient angle accuracy and range detection (coupled withthe receiver).

The present invention is directed to resolving, or at least reducing,one or all of the problems mentioned above.

SUMMARY OF THE INVENTION

In various aspects and embodiments of the present invention, incidentelectromagnetic radiation is received through a subwavelength aperturein a lens, the subwavelength aperture being defined by a substrateencased in a dielectric medium.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention may be understood by reference to the followingdescription taken in conjunction with the accompanying drawings, inwhich like reference numerals identify like elements, and in which:

FIG. 1 depicts one scenario in which the present invention may beemployed in one particular embodiments;

FIG. 2A-FIG. 2B illustrate alternative implementations of the embodimentin FIG. 1 in semi-active and active systems;

FIG. 3A-FIG. 3C depict one particular implementation of the platform inFIG. 1 in a plan, head-on view; a plan, side view; and a partiallysectioned side view, respectively, the view in FIG. 3C being taken alongthe line 3C-3C in FIG. 3A;

FIG. 4A-FIG. 4C are enlarged views of a lens first shown in FIG. 3A-FIG.3C in the same views as in FIG. 3C-FIG. 3C;

FIG. 5A-FIG. 5D conceptually illustrate alternative implementations ofthe periodic surface feature of the substrate of the lenses shown inFIG. 4A-FIG. 4C;

FIG. 6A-FIG. 6B illustrate and alternative implementation for thelensing system of the platform first shown in FIG. 3A-FIG. 3C;

FIG. 7 depicts the detection of the target designation and control ofthe flight control mechanisms of the platform first shown in FIG. 1;

FIG. 8 depicts a controller first shown in FIG. 7 on board the platformof FIG. 1;

FIG. 9A-FIG. 9B illustrate the relationship between angle of incidenceand transmission of radiation impinging on the lenses of the radomeshown in FIG. 1;

FIG. 10A-FIG. 10B illustrate one particular embodiment of asubwavelength aperture monopulse conformal antenna;

FIG. 11A-FIG. 11B conceptually illustrate surface plasmons at a metalsurface;

FIG. 12 shows dispersion relations as to radian frequency versuswavenumber for light in a vacuum, light in a transparent medium, andsurface plasmons, respectively;

FIG. 13A-FIG. 13C illustrate the effect of corrugation and surfaceplasmon generation;

FIG. 14 illustrates assorted incident plane, vector & angle definitions;

FIG. 15 illustrates k-Space for n₁<n₂;

FIG. 16A-FIG. 16B illustrate k-Space for n₁>n₂ and critical angle;

FIG. 17 illustrates evanescent wave amplitude;

FIG. 18 is a cross-section of a circular grating and the diffraction ofan incident beam;

FIG. 19A-FIG. 19B illustrate incident E-field at metal and metamaterialinterfaces, respectively;

FIG. 20 graphs subwavelength aperture diameter versus index ofdielectric layer and radio frequency employed;

FIG. 21A-FIG. 21B depicts a subwavelength aperture and bull's eyegrating used in investigating several physical responses;

FIG. 22A-FIG. 22D illustrate three different surfaces used in theinvestigation depicted in FIG. 21;

FIG. 23A-FIG. 23D graph E-field enhancement as a function of grooveposition, groove depth, groove width, and number of rings for use ingroove tuning;

FIG. 24 illustrates an experimental test setup;

FIG. 25 graphs a transmission enhancement factor as a function offrequency for the structure of FIG. 22C;

FIG. 26A-FIG. 26B depicts modeled H & E fields at resonance;

FIG. 27 depicts a modeled time averaged E-field at a grating top surface(z=0);

FIG. 28 illustrate enhancement and beam narrowing resulting from gratingthe illumination and exit sides of the plate in FIG. 21A;

FIG. 29A-FIG. 29B depict an aperture exit power pattern with a gratingoutside surface only and a grating both sides, respectively;

FIG. 30A-FIG. 30C show the effect of grating period errors about asubwavelength aperture at optical wavelengths;

FIG. 31A-FIG. 31B graphs exit power reduction with incidence variationand plots the transmission amplitude as a function of incident angle;

FIG. 32 graphs the grating period versus index and frequency;

FIG. 33 graphs Fresnel transmittance versus index of refraction andincident angle;

FIG. 34A-FIG. 34C graphs a variety of quantities;

FIG. 35 graphs subwavelength evanescent coupling loss versus frequency,diameter, index; and

FIG. 36 graphs received peak power versus range, index, and aperture.

While the invention is susceptible to various modifications andalternative forms, the drawings illustrate specific embodiments hereindescribed in detail by way of example. It should be understood, however,that the description herein of specific embodiments is not intended tolimit the invention to the particular forms disclosed, but on thecontrary, the intention is to cover all modifications, equivalents, andalternatives falling within the spirit and scope of the invention asdefined by the appended claims.

DETAILED DESCRIPTION OF THE INVENTION

Illustrative embodiments of the invention are described below. In theinterest of clarity, not all features of an actual implementation aredescribed in this specification. It will of course be appreciated thatin the development of any such actual embodiment, numerousimplementation-specific decisions must be made to achieve thedevelopers' specific goals, such as compliance with system-related andbusiness-related constraints, which will vary from one implementation toanother. Moreover, it will be appreciated that such a developmenteffort, even if complex and time-consuming, would be a routineundertaking for those of ordinary skill in the art having the benefit ofthis disclosure.

FIG. 1 illustrates one particular embodiment 100 of the presentinvention. In the embodiment 100 of FIG. 1, a platform 103 receivesradiation 106, from a target 109. The implementation of the platform 103is not material to the practice of the invention although the inventionis particularly suited for use in compact, high-speed platforms, such asmissiles. Similarly, the implementation of the target 109 is notmaterial to the practice of the invention. However, given its particularsuitability, is particularly useful against certain types of targetssuch as, for example, a rocket propelled grenade (“RPG”) or a freespacemortar.

The radiation 106 is typically a bandwidth of interest for the platform103. It therefore usually is known a priori, i.e., a bandwidth centeredon the frequency of the radiation 106. In various alternativeembodiments, the received energy may be in any of several bands,including—but not limited to—the visible, ultraviolet (“UV”), nearinfrared (“NIR”), medium-wavelength infrared (“MWIR”) andlong-wavelength infrared (“LWIR”) bands, whether these wavelengthsoriginate from laser designation or by virtue of radiation emitted bythermally hot targets, or through some other mechanism. In theillustrated embodiment, the radiation 106 is a radio frequency (“RF”)signal, e.g., a RADAR signal.

The frequency of the radiation 106 will depend to some degree on otherimplementation specific factors. As an example, the invention may beused in passive, semi-active, or active system. For present purposes, apassive system would be one in which the radiation 106 emanates from thetarget 109. A semi-active system, such as the one in FIG. 2A, is one inwhich the radiation 106 originates from a source 200 off-board theplatform 103 and is reflected from target 109 to the platform 103. Anactive system, such as the one shown in FIG. 2B, is one in which theradiation 106 originates from a source (203) on-board the platform 103and is reflected from target 109 back to the platform 103. Active andsemi-active systems such as those shown in FIG. 2A-FIG. 2B generallyemploy radio frequency or optical frequency signals while passivesystems may use signals drawn from a wider range of frequencies.

FIG. 3A-FIG. 3C depict one particular implementation of the platform inFIG. 1 in a plan, head-on view; a plan, side view; and a partiallysectioned side view, respectively, the view in FIG. 3C being taken alongthe line 3C-3C in FIG. 3A. The forward end of the platform 103 comprisesa radome 300. The radome 300 of the illustrated embodiment is alsofabricated from a suitable metal in a manner well known to the art.However, other embodiments may employ other materials, such asdielectric materials like those used to implement the lenses 301, 302,as discussed below. Note that embodiments employing dielectric materialsrather than a metal will not exhibit the surface plasmon polaritoneffect discussed below, but that the diffraction that is also discussedfurther below will still occur.

The radome 300 in the illustrated embodiment is a “sleek” radome, suchas a von Karman or an Ogive radome. In alternative embodiments, theradome 300 may be a “blunt” radome, such as a semi-spherical orhemispherical radome. However, the choice does have some impact on theimplementation of other aspects of the platform 103, as will bediscussed further below.

One reason the illustrated embodiment employs a sleek radome 300 isbecause it also employs a non-coherent Fresnel direction finding(“NCFDF”) technique. As will be described more fully below, and asdescribed in the '645 patent incorporated above, the NCFDF techniquerelies on high incident angles between the received radiation 106, shownin FIG. 1, and the radome 300. It also relies on overlapping fields ofview, which can also be accommodated by a sleek radome. Unlike typicalantennas, however, the NCFDF technique is independent of the baselinebetween the lenses 301, 302. Regardless, a platform employing NCFDFshould present strong incident angles to the oncoming wave and come inpairs for targets of unknown amplitude variation.

Another consequence of the sleek radome 300 is that the lenses 301, 302are “foreshortened” from the vantage point of the received radiation106. Thus, to the approaching radiation 106, the lenses 301, 302 appearto be smaller than they really are. It is the apparent size, however,that determines the amount of radiation in the approaching wave frontthat is actually received and detected. As the design of the radome 300becomes more sleek, the more the foreshortened the lens becomes and themore signal that is rejected.

The sleekness of the radome 300 therefore presents a tradeoff to thesystem designer. A more sleek radome 300 improves the accuracy of theNCFDF while increasing the amount of the received radiation that isrejected. Other design constraints may also impact the tradeoff, such asvelocity, weight, and size constraints, in a manner that will beapparent to those skilled in the art having the benefit of thisdisclosure. For the illustrated embodiment, the dielectric material usedto implement the lenses 301, 302 as discussed further below may alsoimpact the tradeoff. In general, however, the illustrated embodimentbenefits from a high degree of sleekness for the radome 300 yielding aconcomitant high degree of lens foreshortening.

A plurality of lenses 301-302 are situated in the radome 300. The numberof lenses is not material to the practice of the invention, but will bea consideration in any given embodiment. The lenses 301-302 are opposed,forward looking lenses in the region in which their fields of viewoverlap. The lens 301 is shown in enlarged views in FIG. 4A-FIG. 4C inthe same views as in FIG. 3A-FIG. 3C. Note that, in this particularembodiment, the lens 302 has the same construction as the lens 301, andso is not shown. The lens 301 comprises a substrate 400 encased by adielectric medium 403, shown in two parts for the sake of clarity inFIG. 4A.

The substrate 400 is, in the illustrated embodiment, fabricated from ametal. Simple metals, such as silver, should work well. However,alternative embodiments may employ other materials. For example, thesubstrate may be fabricated from a semiconducting material such asGermanium, whether intrinsic or doped. These embodiments will notgenerate the Plasmon polaritons relied upon in some embodiments forenhancement of the incident radiation.

The dielectric medium 403 may be fabricated from practically anydielectric material, such as plastic, fused silica, or diamond and fluidmaterials such as air may be used. In the illustrated embodiment, thedielectric medium is a solid sold under the mark RT DUROID 5870available from Rogers Corporation, One Technology Drive, PO Box 188,Rogers, Conn. 06263-0188 and may be contacted at 860.774.9605 (phone) or860.779.5509 (fax) or from their website athttp://www.rogerscorporation.com/. This material is a glass microfiberreinforced polytetrafluoroethylene (“PTFE”) composite and additionalinformation is available on the Internet athttp://www.rogerscorporation.com/mwu/pdf/5000data.pdf#search=‘duroid’.This material has an index of refraction n=1.5.

In the illustrated embodiment, the dielectric medium 403 comprises thesame material on both the illumination and exit sides of the substrate400. This is not necessary to the practice of the invention. In some ofthese embodiments, the different materials may even have differentindices of refraction. Performance constraints or embodiments using theNCFDF technique will typically ensure that a high dielectric materialwill be used. Some embodiments may employ different materials toimplement the dielectric medium 403 on the opposing sides of thesubstrate 400. In general, however, the illustrated embodiment benefitsfrom a high dielectric medium encasing the substrate 400.

The substrate 400 defines a subwavelength aperture 409. The aperture 409is “subwavelength” in the sense that its diameter is dimensioned to beless than the wavelength of the incident energy of interest. Forexample, in the illustrated embodiment, the signal 124 in FIG. 1 is aradio frequency signal, and so the diameter of the aperture 409 is lessthan the wavelength of a radio frequency signal. Radio frequency isgenerally accepted to be between about 3 Hz-300 GHz, which yieldswavelengths between 100,000 km-1 mm. However, the signal of interestwill have a known, narrower range of frequencies to which the dimensionof the aperture 409 may be tailored. As will be apparent to thoseskilled in the art having the benefit of this disclosure, whatconstitutes “subwavelength” will vary with the frequency of the signalof interest. For example, the present invention may be used with opticalfrequencies, which will yield different dimensions for “subwavelength”.

The aperture 409 is countersunk on both the top and bottom faces 412,413 as is shown in FIG. 4A for the illumination side 412. This producesan hourglass-shaped cross-section as is shown in FIG. 4B. This is notrequired for the practice of the invention, however. For example, theaperture 409 may be countersunk on only one of the illumination and exitsides 412, 413. The aperture 409 also may not be countersunk at all inalternative embodiments such that the aperture 409 is a smooth bore.Still other variations on this theme may by practiced in still otherembodiments.

The substrate 400 defines a periodic surface feature generally indicatedat 415 in FIG. 4B. (Note that, because the dielectric medium 403 encasesthe substrate 400, the dielectric medium 403 mirrors the periodicsurface feature 415 on the and faces 417, 418 that contact the substrate400.) The periodic surface features 415 are optional, and may be omittedin some embodiments. However, they generally improve the efficacy of thesubwavelength aperture 409 in terms of the evanescent wave generation.

Where employed, the periodic surface feature 415 may take many forms.Gratings, bumps, posts, divots, and roughness all may work in variousalternative embodiments. In the illustrated embodiment, the periodicsurface feature 415 comprises a plurality of arcuate ridges, such as thearcuate grooves 500 (only one indicated), conceptually depicted in FIG.5A. FIG. 5B illustrates an alternative implementation of the surfacefeature 415 comprising a plurality of linear grooves 503 (only oneindicated). FIG. 5C illustrates an implementation in which lineargrooves 506, 509 (only one of each indicated) that radiate in orthogonaldirections. In the illustrated embodiment, these directions would beparallel and transverse to the longitudinal axis of the platform 103.FIG. 5D illustrates an implementation in which the periodic surfacefeature 415 comprises a plurality of concentric rings 512. Note that theperiodic surface feature 415 may be implemented using both negative andpositive features, e.g., grooves and/or ridges. The periodic surfacefeature 415 also generally exhibit uniform characteristics, e.g., interms of period (or spacing), height, and width.

The invention admits wide variation in the implementation of theperiodic surface feature(s) 415. Just as the periodic surface feature415 may be omitted altogether in some embodiments, it can be omitted ononly one side of the substrate 400 while being employed on the other.Thus, for example, a periodic surface grating 415 may be formed only onthe face on the illumination side 412 of the substrate 400 and omittedon the face on the exit sides. The illustrated embodiment also employsthe same periodic surface feature 415 on both faces 412, 413—namely, thearcuate grooves shown in FIG. 5A. Alternative embodiments may employdifferent periodic surface features 415 on the illumination and exitsides of the substrate 400.

Note that the implementation of the periodic surface feature may alsoaffect other aspects of the design for the lenses 301, 302. For example,as was mentioned above, some embodiments may omit the periodic surfacefeature 415. The omission will degrade performance to some degree as itwill degrade the coupling discussed further below. To compensate forthis degradation, such embodiments can employ additional apertures 409.Other examples will become apparent to those skilled in the art havingthe benefit of this disclosure.

Returning to FIG. 3A-FIG. 3C, the lenses 301, 302 should also be able towithstand applicable environmental conditions. In the illustratedembodiment, one important environmental condition is aerodynamic heatingdue to the velocity of the platform 103. Another important environmentalcondition for the illustrated embodiment is abrasion, such as thatcaused by dust or sand impacting the lenses 301, 302 at a high velocity.Thus, for the illustrated embodiment, fused silica is a highly desirablematerial for lenses 301, 302. Alternative embodiments may employ ZnSe,Al₂O₃, Ge, Pyrex, diamond, quartz, fused quartz, and glass in additionto the materials discussed above in some embodiments.

Note that the choice of materials will affect other aspects of theimplementation. For example, in some embodiments, the dielectric medium403 encasing the substrate 400, both shown in FIG. 4, may be implementedwith air rather than the DUROID material of the illustrated embodiment.However, if air is used, direction finding is performed from the declinein amplitude vs. angle by “beamwidth” of the subwavelength aperture,while with the higher index dielectrics like DUROID over thesubwavelength aperture, one can employ NCFDF as an enhancement to anglefinding and employ the NCFDF technique that cannot be used for theair-dielectric case. More particularly, NCFDF uses essentially twopieces—Fresnel amplitude vs. angle change and standard amplitudecomparison monopulse sum and difference. Hence, without Fresnel onecould simply use standard amplitude comparison monopulse. As long asthere is a amplitude change with angle change standard amplitudecomparison monopulse can be used.

Depending upon a number of factors, including the shape of the radome300, the strength of the lens materials, manufacturability, and cost, itmay be preferable to implement the lenses 301, 302 collectively as acollar extending around the perimeter of the radome 300. Thus, thelenses 301, 302 comprise a lensing system that, in alternativeembodiments, may be implemented in a collar, such as the collar 600shown in FIG. 6A-FIG. 6B. Thus, the lenses 301, 302 actually comprise alensing system and are but one example of a means for lensing the radome300. Other lensing systems may employ other lensing means in alternativeembodiments.

Referring now to FIG. 3C, the radome 300 houses a pair of feeds 305, onefor each of the lenses 301, 302. The illustrated embodiment is intendedfor use with radio frequencies, and so the feeds 305 are routed to radiofrequency (“RF”) detectors. The feeds 305 will vary in implementationwith the bandwidth of interest of the received radiation with which theplatform 103 is intended to work. Those working at optical frequencieswill implement detectors with optical detectors and those operating atinfrared (“IR”) frequencies will implement them with IR detectors, forexample. Frequency-dependent detectors are well known and commonly usedin the art, and those in the art having the benefit of this disclosurewill appreciate these types of considerations in implementation.

Note the ullage in the chamber 310 defined by the radome 300. This isone of the significant benefits of the present invention in that itreduces the number of components needed to receive and detect theincident radiation. This clears the central axis of the radome 300 forother uses. The illustrated embodiment is a passive system, and so theullage is maximized. In an active system, for example, some of theullage would be consumed by components used in signal generation andtransmission. The ullage can be left void, i.e., filled with air, orplaced under vacuum. It may also be filled with a dielectric material,e.g., such as the material from which the dielectric medium 403 isfabricated. Alternatively, the ullage may be used to house othercomponents of the platform 103, such as signal processing and computingcomponents (not shown). Or, in some embodiments, the ullage could beused to house additional explosives. Note, however, the volume 310cannot be obstructed as RF passed through this region to the RF feed305. The central region may, however, be used for other components.

FIG. 7 conceptually depicts a selected portion 700 of the command andcontrol (“2C”) architecture of the platform 103. The portion 700 depictsa sensor 703, a controller 706, and a flight control mechanism 709. Notethat, as will be appreciated by those skilled in the art having thebenefits of this disclosure, the 2C architecture of the platform 103 ismuch more complex and involved. However, details unrelated to thepresent invention have been omitted for the sake of clarity and so asnot to obscure the present invention.

The sensor 703 comprises those elements of the invention discussed aboverelative to FIG. 3A-FIG. 3C and FIG. 4A-FIG. 4C. The controller 706receives the output 712 of the sensor 703. The controller 706 processesthe output 712 employing the NCFDF technique disclosed in theincorporated '645 patent to determine the location of the target 109relative to the platform 103. In the illustrated embodiment, thecontroller 706 also outputs guidance navigation control (“GNC”) commandsto the flight control mechanism 709 of the platform 103 to direct theplatform 103 to the target 109.

FIG. 8 depicts selected portions of the controller 706, first shown inFIG. 7, in a block diagram. The controller 706 includes a processor 800communicating with storage 806 over a bus system 809. Each of thesecomponents will now be discussed in turn.

The processor 800 may be any suitable processor known to the art. Ingeneral, the controller 706 will handle a fair amount of data, some ofwhich may be relatively voluminous by nature and which is processedquickly. Thus, certain types of processors may be more desirable thanothers for implementing the processor 800. For instance, a digitalsignal processor (“DSP”) may be more desirable for the illustratedembodiment than will be a general purpose microprocessor. In someembodiments, the processor 800 may be implemented as a processor set,such as a microprocessor with a mathematics co-processor.

The storage 806 may be implemented in conventional fashion and mayinclude a variety of types of storage, such as a hard disk and/or randomaccess memory (“RAM”). The storage 806 will typically involve bothread-only and writable memory implemented in disk storage and/or cache.Parts of the storage 806 will typically be implemented in magnetic media(e.g., magnetic tape or magnetic disk) while other parts may beimplemented in optical media (e.g., optical disk). The present inventionadmits wide latitude in implementation of the storage 806 in variousembodiments.

The storage 806 is also encoded with a variety of software components,including an operating system 821, the sensor data 827, a guidancenavigation control (“GNC”) component 830, and a software application833. That is, these software components “reside” on the storage 806. Theprocessor 800 runs under the control of the operating system (“OS”) 821,which may be practically any operating system known to the art. Thecontroller 706 receives the sensor data 827 from the sensor 703 (shownin FIG. 7) and stores it on the storage 806. The sensor data 827 may bestored in any suitable type of data structure known to the art, such asfirst-in, first-out (“FIFO”) queue. The GNC component 830 issuessuitable GNC commands to the flight control mechanism 709 as mentionedabove. The nature of the GNC commands will be dependent on theimplementation of the flight control mechanism 709, which is furtherdiscussed immediately below.

Returning to FIG. 7, the flight control mechanism 709 is shown ascomprising a plurality of flight control surfaces 721—i.e., fins—andtheir actuators 724. As will be appreciated by those in the art havingthe benefit of this disclosure, many types of flight control mechanismsmay be employed. Many of these types, such as fins and canards, employflight control surfaces. Others do not, however. For instance, someweapons might employ thrusters in addition to or in lieu of flightcontrol surfaces. The invention is not limited by the nature of theflight control mechanism employed. Similarly, the number of componentswithin the flight control mechanism 709 is not material. For instance,the platform 103 might employ three, four, or more flight controlsurfaces 721 or as many as 12 thrusters. Furthermore, the flight controlmechanism 709 may be located aft (as shown), forward, or both aft andforward of the platform 103, depending in the implementation. Thus, theflight control surfaces 721 are, by way of example and illustration, butone means for controlling the flight of the platform 103 in accordancewith the present invention.

Returning again to FIG. 8, the software application 833 analyzes thesensor data 827 to determine the location of the target 109. In theillustrated embodiment, if the software application 833 detects a changein position for the target 109, the software application 833 notifiesthe GNC component 830. The GNC component 830 then issues commands to theflight control mechanism 709 to alter the heading of the platform 103 tomaintain an intercept course with the target 109. The softwareapplication 833 may constitute a constituent part of the GNC component830 in some embodiments, or may constitute a stand alone softwarecomponent interfaced with the GNC component 830.

As is apparent from the discussion above, some portions of the detaileddescriptions herein are presented in terms of a software implementedprocess involving symbolic representations of operations on data bitswithin a memory in a computing system or a computing device. Thesedescriptions and representations are the means used by those in the artto most effectively convey the substance of their work to others skilledin the art. The process and operation require physical manipulations ofphysical quantities. Usually, though not necessarily, these quantitiestake the form of electrical, magnetic, or optical signals capable ofbeing stored, transferred, combined, compared, and otherwisemanipulated. It has proven convenient at times, principally for reasonsof common usage, to refer to these signals as bits, values, elements,symbols, characters, terms, numbers, or the like.

It should be borne in mind, however, that all of these and similar termsare to be associated with the appropriate physical quantities and aremerely convenient labels applied to these quantities. Unlessspecifically stated or otherwise as may be apparent, throughout thepresent disclosure, these descriptions refer to the action and processesof an electronic device, that manipulates and transforms datarepresented as physical (electronic, magnetic, or optical) quantitieswithin some electronic device's storage into other data similarlyrepresented as physical quantities within the storage, or intransmission or display devices. Exemplary of the terms denoting such adescription are, without limitation, the terms “processing,”“computing,” “calculating,” “determining,” “displaying,” and the like.

Note also that the software implemented aspects of the invention aretypically encoded on some form of program storage medium or implementedover some type of transmission medium. The program storage medium may bemagnetic (e.g., a floppy disk or a hard drive) or optical (e.g., acompact disk read only memory, or “CD ROM”), and may be read only orrandom access. Similarly, the transmission medium may be twisted wirepairs, coaxial cable, optical fiber, or some other suitable transmissionmedium known to the art. The invention is not limited by these aspectsof any given implementation.

Thus, in operation, the platform 103 receives radiation 106, from atarget 109 as shown in FIG. 1. The radiation 106 impinges upon theforeshortened lenses 301, 302, shown in FIG. 3A-FIG. 3C, at a high angleof incidence engendered by the sleek profile of the radome 300. Theradiation 106 propagates through the dielectric medium 403, shown inFIG. 4A-FIG. 4C, the subwavelength aperture 409 of the substrate 400,and the chamber 310, shown in FIG. 3C defined by the radome 300, whereit is intercepted by the feed 305.

The propagation of the radiation 106 through the subwavelength apertures409 creates “evanescent waves”. Below their cut-off frequency thesubwavelength apertures 409 are too small to pass longer waves—which iswhat “cut-off” means—as antennas normally do. The subwavelengthapertures 409 therefore, in a manner of speaking, force waves too longto get through the apertures 409 anyway by “squeezing” the radiation 106into the subwavelength apertures 409 as evanescent waves. The evanescentwaves create a condition shown in FIG. 19A-FIG. 19B and described morefully below. Essentially, this condition looks like a “surface wave”phenomena. Such surface waves, or surface mode phenomena includeplasmons and polaritons. The substrate 400 becomes a “meta material”,which is a class of materials that has a negative index of refraction,as discussed further below.

Thus, the feeds 305 detect radio waves emergent from the evanescentwaves generated when the radiation 106 impinges upon the subwavelengthapertures 409. The detected radiation is then processed by thecontroller 706, shown in FIG. 7 using the NCFDF technique disclosed inthe incorporated '645 patent. In this technique, the magnitude of thetransmitted radiation decreases as a continuous function of increasingangle of incidence, known as Fresnel transmittance. Opposing radiationdetectors then detect this transmitted radiation as discussed above,thereby creating a pair of detection signals. By dividing the differenceof the detection signals by the sum of the detection signals, theprocessor 800, shown in FIG. 8, of the controller 706 generates a betaangle error curve and finds the relative direction of the radiation.

More particularly, as seen in FIG. 8A, the transmittance of radiation,as a percentage, through an air/fused silica interface is a strongfunction of both incidence angle and polarization based upon Fresnel'sequations:

t _(s)=2n _(i) cos(θ_(i))/[n _(i) cos(θ_(i))+n _(i) cos(θ_(t))],and  (1)

t _(p)=2n _(i) cos(θ_(i))/[n _(i) cos(θ_(t))+n _(t) cos(θ_(i))].  (2)

In Fresnel's equations, Eq. (1) and Eq. (2), t_(s) corresponds to thetransmittance for S-polarized (perpendicular) radiation and t_(p)corresponds to the transmittance for P-polarized (parallel) radiation.θ_(i) and θ_(t) correspond to the angles of incidence and transmission,respectively. Lastly, n_(i) and n_(t) correspond to the indices ofrefraction for the incident and transmitted materials, respectively.This dependence of the transmittance upon the angle of incidence shallbe defined as Fresnel transmittance.

Curve 902 approximates the Fresnel transmittance ts for radiationincident upon the air/fused silica interface, while curve 904approximates the Fresnel transmittance t_(p). At low angles, such aspoint 910 at 10°, corresponding to a blunt or hemispherical radome,Fresnel transmittance is not a strong function of angle at all. Morespecifically, for an incident angle of 10°, radiation received within anangle of +10° (point 912) to −10° (point 914) shows virtually nodifference in Fresnel transmittance, regardless of polarization. Incontrast, an incident angle of 70° (point 820), corresponding to arelatively sleek radome, shows significant differences in Fresneltransmittance for angles ±10°.

Specifying a middle field of view transmittance is an alternative methodfor defining a direction finding system design and is illustrated inFIG. 9B. For example, for a middle field of view Fresnel transmittanceof 90% for P-polarized radiation (point 930), a ±10° field of viewprovides a change in Fresnel transmittance of approximately 50% (points932 and 934). A middle field of view Fresnel transmittance of 80% forS-polarized radiation (point 940) provides a change in Fresneltransmittance of approximately 25% (points 942 and 944) over the ±10°field of view. A middle field of view Fresnel transmittance of 70% wouldbe preferable for the S-polarized radiation (point 950) as the ±10°field of view change in Fresnel transmittance increases to 40% (points952 and 954). Because of this continuous or smooth variation in Fresneltransmittance as a function of incidence angle, even a single radiationdetector can provide some indication of the angle of incidence ifproperly calibrated. However, at least three radiation detectors arepreferred to provide the level of control desired for a precision guidedmunitions traveling at a high velocity.

Thus a sleek radome system benefiting from the Fresnel transmittance hasa greater angular sensitivity than a blunt or hemispherical radomesystem. To benefit from the Fresnel transmittance, the incidence angleshould be selected such that the Fresnel transmittance of the radiationvaries significantly over the desired field of view, i.e., the slope ofthe Fresnel transmittance is significantly difference from zero. Theabove example employed a field of view of ±10° and a fused silica-basedmaterial for the lenses 301, 302. Under these conditions, a minimumangle of incidence at boresight of at least approximately 60° ispreferred, with at least approximately 60° being more preferred. Themaximum incidence angle is approximately 80° when a ±10° field of viewis used.

Note that these minimum and maximum incidence angles are a function ofthe lens material and the field of view. Narrower fields of view willrequire greater minimum angles to ensure that the Fresnel transmittancevaries significantly over the desired field of view. Based uponFresnel's equations, Eq. (1) and Eq. (2), different indices ofrefraction will change the shape of the Fresnel transmittance curve, andthus the minimum angle of incidence. For example, Al₂O₃ has a greaterindex of refraction than fused silica, and therefore would require asmaller minimum angle of incidence. One of skill in the art willappreciate that these and other system parameters, including detectorsensitivity, will determine how great the instantaneous rate of changeof the Fresnel transmittance as a function of angle of incidence wouldneed to be to achieve a required angle sensitivity.

Based upon the beta angle error curve, the processor 800 generates anappropriate error correction signal for guiding the platform 103 basedupon the relative direction of the received radiation. The correctionsignal is translated by the GNC component 830 into control signals forthe actuators 724 of the flight control surfaces 721. This results in acourse correction for the platform 103 to keep it on an intercept coursefor the target 109. The process iterates and is performed continually asthe platform 103 homes on the target 109 until intercept occurs.

The present invention therefore provides one or more of surface areareduction, volume reduction, power enhancement servicing detection rangein a radome surface conformal solution with cleared axis, in its variousaspects and embodiments. Note that not all embodiments will necessarilymanifest all these features. However, by leveraging enhancedtransmission through subwavelength apertures the loss they engender canbe offset (at least in part) and the size of subwavelength aperturessatisfies area/volume restrictions. Joining the aperture's power patternwith the Non-Coherent Fresnel Direction Finding (“NCFDF”) monopulseangle finding technique provides the same accuracy (or slightly better)as the aperture/wavelength independent method provided by NCFDF alone.In addition, the dielectric medium (in which NCFDF takes place) allowsfor size reduction of metal surface features (an inverse proportion)that provide signal enhancement at the expense of added signal lossproportional to refraction index.

Thus, in selected aspects, the present invention:

-   -   employs subwavelength apertures as antennas at either radio or        optical frequency wavelengths;    -   enhances transmitted evanescent signal by surface gratings;    -   satisfies demanding radome surface area/volume constraints of        new, more demanding applications;    -   provides a sleek radome conformal antenna;    -   yields a small profile;    -   facilitates a miniature on-board missile seeker because of the        small profile;    -   frees radome volume to much needed motor and lethality;    -   is polarization “insensitive” for larger radomes; and    -   permits all weather operation at radio frequency wavelengths.        Note that not all embodiments will manifest each or all of these        aspects and that some embodiment may exhibit other aspects not        set forth above.

And now, to further an understanding of the present invention, a moretechnical exposition of the principles underlying the design of theembodiments disclosed above will be set forth. The present invention inthe particular embodiment discussed here employs angle dependenttransmissivity of subwavelength apertures by virtue of evanescent wavediffraction with slight signal enhancement by surface plasmons. Themeasured effects of evanescent coupling through subwavelength aperturesand pseudo-standing wave effects of diffraction allowing enhancement areused here to implement an angle measurement antenna system with highback lobe rejection in the radio spectrum. While the method andapparatus described is most concerned with radio waves, any part of thespectrum including optical will satisfy the method as long as designparameters of the device are accounted for versus wavelength.

FIG. 10A-FIG. 10B illustrate the particular embodiment 1000. The physicsof surface plasmon polaritons will be discussed in association with FIG.11A-FIG. 13. The generation of evanescent waves and their relation tosurface Plasmon polaritons is discussed in association with FIG. 14-FIG.17. FIG. 19-FIG. 20 illustrate the effects of the periodic surfacefeatures. FIG. 21A-FIG. 30B illustrate additional aspects of evanescentwave enhanced transmissivity.

The present discussion will be framed in the context of the embodiment1000 of FIG. 10A-FIG. 10B. This embodiment 1000 uses a single aperture1003 (only one indicated) per lens 1006 because of implementationspecific size constraints. This particular embodiment includes 1.25″base diameter Von Karman radome 1009, and X-band illuminator. Sizeconstraints are exacerbated when using concentric gratings such as theconcentric rings 1008 (only one indicated) used in this particularembodiment given that resonance requires their period be on the order ofthe incident wavelength. Due to the common nature of electromagnetictheory, with some room for differences, phenomena observed in theoptical regime have been shown to be scaleable to the microwave withreasonable accuracy. See Schuchinsky, et al., “Enhanced Transmission inMicrowave Arrays of Periodic Sub-Wavelength Apertures”, J. Opt. A.: Pureand Applied Optics S102-S109 (January 2005).

This particular embodiment employs the “plasmon physics” of plasmonpolaritons. A discussion of the theoretical underpinnings for thisphenomenon follows in association with FIG. 11A-FIG. 20. Couplingelectromagnetic energy, such as the incident radiation 106, shown inFIG. 1 to surface plasmon polaritons leverages their signal enhancement.Note the term “surface plasmon polariton” is used versus “surfaceplasmon” to avoid confusion with surface electrical currents known bythis later description.

Surface plasmon polaritons result from freespace electromagnetic wavescoupling to free electron oscillations (surface plasmons) in metals orsemiconductors. As previously noted, some embodiments may havesubstrates fabricated from materials other than metals orsemiconductors. However, these embodiments will not exhibit thegeneration of plasmon polaritons discussed here. Surface plasmonpolaritons are essentially light waves trapped on the surface due totheir interaction with electrons on the conductor—in this case light issaid to be converted to the plasmon mode. Barnes et al., “SurfacePlasmon Subwavelength Optics”, Nature, 424, 6950, pg 824-830 (Aug. 14,2003). Since metals or semiconductors support collective surfaceoscillations of free electrons, these collections can concentrateelectromagnetic fields on the nanoscale, enhancing local field strengthby several orders of magnitude. Plasmon characteristics can be accessedat optical and radio wavelengths.

The concept of surface plasmons originates in the plasma approach toMaxwell's equations. Atoms in mass such as metals have valence electronsthat become conduction electrons approximately free to move aboutwithout collisions, known as a free-electron gas because they move likemolecules in an ideal gas (sometimes referred to as an electron liquid).A free-electron gas is a plasma (not plasmon). As in any gas,longitudinal modes can be excited (like sound waves in air). Thequantization of this longitudinal plasma wave (a density fluctuation) iscalled a plasmon or surface plasmon when the modes are confined aselectrical currents on a smooth surface.

Referring now to FIG. 11A-FIG. 11B, FIG. 11A illustrates the behavior ofsurface plasmons at the interface 1100 between a metal 1103 and adielectric 1106. Though resulting from electron density fluctuations,surface plasmons represent electromagnetic surface waves with theirintensity maximum in the surface which exponentially decay away fromthat surface as shown in FIG. 11B. Notice in FIG. 11A that surfaceplasmons have a definable wavelength. While normal propagatingelectromagnetic (“EM”) waves have constant phase and amplitude in thesame plane, waves such as those shown in FIG. 11A-FIG. 11B have planesof constant phase perpendicular to the interface, as shown in FIG. 11A,and planes of constant amplitude parallel to that interface, as shown inFIG. 11B.

Any dielectric material experiencing the forces of electromagnetic wavesfind their internal charge distribution separated, resulting in electricdipole moments which in turn contribute to the incident EM field.Primary responders are electrons followed by polar molecules. Even lowinertia electrons fail to keep up with high frequencies at some pointdepending on material. This dependence is described by the index ofrefraction (or dielectric constant or relative permittivity) and is afunction of EM frequency ω. This dependence on index (or k, explainedbelow) and on frequency ω (or wavelength λ) is called a “dispersionrelation”. (Recall that different colors of visible light travel atdifferent speeds and bend at different angles in the same prism creatinga rainbow—an expression of dispersion—because different λ's experiencedifferent index.)

FIG. 12 shows several dispersion relations as ω (radian frequency)versus k (wave-number) for light in vacuum as ω=ck (trace 1200); lightin some transparent medium with index of refraction n such that ω=ck/n(trace 1203); and that of surface plasmons (trace 1206), where ω_(P) isthe plasma frequency of electrons in the material. Surface plasmons lieto the right of the freespace light line ω=ck implying that surfaceplasmons have shorter wavelengths than light. Since freespace light, ck,and surface plasmon dispersion relations do not intersect, light cannotdirectly excite (resonate) surface plasmons and surface plasmons cannotspontaneously radiate light. For a given frequency of freespace lightthe wavelength is set by c=λf, but for the same given frequency surfaceplasmons have some other λ and thus do not satisfy c=λf.

Surface plasmons feel the effects of both media—the dielectric 1106 andthe metal 1103, both shown in FIG. 11A. The surface plasmon wavelengththen depends on properties of both materials at the interface ofinterest through the dispersion relation in terms of wavelength by

$\begin{matrix}{\lambda_{sp} = {\lambda \left\lbrack \frac{ɛ_{m} + ɛ_{d}}{ɛ_{m}ɛ_{d}} \right\rbrack}^{\frac{1}{2}}} & (3)\end{matrix}$

where ε is the relative permittivity or dielectric constant in a metal mor dielectric d (√{square root over (ε)}=n the index of refraction). Formetals, ε_(m) can be negative and both ε_(m) and ε_(d) are complex wherethe imaginary term quantifies absorption loss (though the imaginarycomponent of ε_(d) is usually ignored for linear materials except underextreme conditions of high power). The dielectric function of a metal isε_(m)=ε′+iε″ and if we assume that ε″<|ε′| we can create a complexk_(sp)=k′_(sp)+ik″_(sp) where a surface plasmon wave-number has real andimaginary components.

Eq. (4) below is the same as Eq. (3) above, although expressed in termsof wave number k=2π/λ.

$\begin{matrix}{k_{sp}^{\prime} = {\frac{\omega}{c}\left\lbrack \frac{ɛ_{m}^{\prime}ɛ_{d}}{ɛ_{m}^{\prime} + ɛ_{d}} \right\rbrack}^{\frac{1}{2}}} & (4)\end{matrix}$

$\begin{matrix}{k_{sp}^{''} = {{\frac{\omega}{c}\left\lbrack \frac{ɛ_{m}^{\prime}ɛ_{d}}{ɛ_{m}^{\prime} + ɛ_{d}} \right\rbrack}^{\frac{3}{2}}\left\lbrack {2\; ɛ_{m}^{''\; 2}} \right\rbrack}} & (5)\end{matrix}$

Raether, “Surface Plasmons on Smooth and Rough Surfaces and on Gratings”(Springer-Verlag, 1988). For real k′_(sp), we need ε′_(m)<0 and|ε′|>ε_(d), which is fulfilled by metals, such that, while ε′_(m) has anabsolute value greater than ε_(d), ε′_(m) and ε_(d) have opposite signs.Note that the surface plasmon frequency is

$\begin{matrix}{\omega_{sp} = \left\lbrack \frac{\omega_{p}}{1 + ɛ_{d}} \right\rbrack^{\frac{1}{2}}} & (6)\end{matrix}$

where ω_(P) is the plasma frequency under the assumption of a freeelectron gas. As the dielectric ε_(d) increases, light λ in a dielectricmaterial decreases as k for light in that medium goes up. But from Eq.(6) the surface plasmon frequency decreases (its λ increases). Implicithere is a potential match between the k's of both light and surfaceplasmons.

For the case of surface plasmons on a smooth planar metal, they displaynon-radiative electromagnetic modes, that is, surface plasmons cannotdecay spontaneously into photons nor can light be coupled directly withsurface plasmons. The reason for this non-radiative nature of surfaceplasmons is that interaction between light and surface plasmons cannotsimultaneously satisfy energy and momentum conservation. In other words,the requirement for conservation of parallel momentum is not satisfiedas represented by the momentum wave-vector k (its magnitude being k asnoted, or more specifically k_(z) along the horizontal z-plane definedby the dielectric/metal interface). “Spectroscopy of Gap Modes in MetalParticle-Surface Systems”, Shinji Hayashi, pg 81, in “Near-Field Opticsand Surface Plasmon Polaritons” (Satoshi Kawata Ed.) Springer, 2001).

When surface plasmons and light are made to be in resonance, the resultis a “surface plasmon polariton” (surface plasmon polariton)—anelectromagnetic field in which both light and electron wavedistributions match in their k_(z) momentum vector—they have the samewavelength. Resonance and field enhancement can be made to take place ifthe light momentum wave-vector k_(z) is increased as in a transparentmedium with index of refractive n (trace 1102 FIG. 12) to match thesurface plasmon momentum z-component wave-vector k_(sp), or inverselyresonance can be achieved by roughening the metal surface to decrease asurface plasmon's z-component k_(sp) in order to match that of freespacelight k_(z).

In practice, momentum restrictions are circumvented by either a prismcoupling technique (to shorten light λ thus increasing its k_(z)), or bya metal surface grating, nano-structures such as holes, dimples, postsor statically rough surfaces (to lengthen surface plasmon λ thusdecreasing its z-component k_(sp)). See Middle Tennessee UniversityPhysics Department, at http://physics.mtsu.edu/˜wmr/surfplas.htm,http://www.mtsu.edu/˜physics/.

The corrugated method to matching is shown in FIG. 13A. The two prismcoupling methods in FIG. 13A-FIG. 13B are known as attenuated totalreflection (“ATR”), where incident electromagnetic radiation 1300, 1303is passed through an optically dense medium, increasing its wave-vectorfrom what it was in air (a dielectric medium). This beam 1300 thenreflects off the boundary 1306 between an optically less dense medium asin a narrow air gap (Otto configuration, FIG. 13B), or penetrates ametallic layer on the prism backface (Kretchmann-Raether configuration,FIG. 13C).

Turning now to generation of evanescent waves, production of photonevanescent waves is described graphically by the k-vector approach shownin FIG. 14. A fuller discourse on the production of photon evanescentwaves is presented in co-pending U.S. application Ser. No. 11/288,630,entitled “Evanescent Wave Coupling for Fresnel Direction Finding,” filedin the name of Brett A. Williams (the '630 patent) and commonly assignedherewith. This application is hereby incorporated by reference as ifexpressly set forth verbatim herein. A shorter disclosure excerptedtherefrom shall now be presented in order to further an understanding ofthe present invention.

FIG. 14 presents the arrangement of incident (i), reflected (r), andtransmitted (t) energy. Each k-vector is defined in terms of itscomponent in x and z with unit vectors for each axis as (positive x up,positive z right):

k _(i) =− xk _(ix) + z _(iz)  (7)

k _(r) =− xk _(rx) + z _(rz)  (8)

k _(t) =− xk _(tx) + z _(tz)  (9)

The projections of each k by sin and cosine can be seen from thedrawing.

k_(ix)k₁ cos θ_(i)=k_(iz)=k₁ sin θ_(i)  (10)

k_(rx)k₁ cos θ_(r)=k_(rz)=k₁ sin θ_(r)  (11)

k_(tx)k₁ cos θ_(t)=k_(tz)=k₁ sin θ_(r)  (12)

where k₁ and k₂ are k for their medium. Given that Maxwell's boundaryconditions require continuous tangential components across that boundary(conservation of momentum vector), and that k is the same for bothincident and reflected, this then means θ_(i) and θ_(r) must be the sameand that:

k₁ sin θ_(i)=k₂ sin θ_(t)  (13)

which is Snell's Law derived from Maxwell's phase matching.Additionally, if the waves in both Region 1 and Region 2 must satisfythe following dispersion relations:

$\begin{matrix}{k_{1} = \sqrt{k_{ix}^{2} + k_{iz}^{2}}} & (14) \\{k_{2} = \sqrt{k_{tx}^{2} + k_{tz}^{2}}} & (15)\end{matrix}$

which are equations for a circle, then one can graphically display whathappens in k-space when k₁<k₂ (index n₁<n₂) as shown in FIG. 15. Sincethe z-components of all k's are equal by Maxwell's requirement at theinterface and n₁<n₂ then the magnitude of k₂ (2πn₂/λ) (also k_(t) in theFIG. 15) is greater than k₁ and each traces out a half-circle in theirrespective region as shown.

The case where n₁>n₂, as shown in FIG. 16A-FIG. 16B is of most interesthere. Note that the z-component of k₁ exceeds that of k₂ at and afterthe critical angle θ_(c) where θ_(t)=90°.

Finally one can ask what happens to k when θ_(i)>θ_(c) with n₁>n₂, whichanswered from the classical optics standpoint is, nothing. From thedispersion relation of Eq. (15) above, solving for k_(tx) (down, intothe next medium) one gets,

$\begin{matrix}{k_{tx} = \sqrt{k_{2}^{2} - k_{tz}^{2}}} & (16)\end{matrix}$

Because of Maxwell's phase matching k_(tz)=k₁ sin θ_(i) (projection ofk₁ on z-axis) so that:

$\begin{matrix}{k_{tx} = \sqrt{k_{2}^{2} - {k_{1}^{2}\sin \; \theta_{i}^{2}}}} & (17)\end{matrix}$

Note that k₁ sin θ_(i)=k₂ at θ_(c) (FIG. 16B because θ_(r) substitutesfor θ_(i) given they're equal). If k₁ sin θ_(i)>k₂ then the square rootis negative and k_(tx) becomes imaginary.

$\begin{matrix}{k_{tx} = {{{\pm j}\sqrt{{k_{1}^{2}\sin \; \theta_{i}^{2}} - k_{2}^{2}}} \equiv {\pm {j\alpha}_{tx}}}} & (18)\end{matrix}$

The wave variation in Region 2 is of the form, see the '630 application,supra, (here along the x-axis)

e^(jk) _(tx) ^(x)=e^(j(±jα) ^(tx) ^()x)=e^(±α) ^(tx) ^(x)  (19)

Since physically this function must not go to infinity when x goes to −∞the last term on the right is made to satisfy this requirement by achoice of positive sign in Eq. (19) and

k_(tx)=−ja_(tx), when θ_(i)>θ_(c)  (20)

At last, Eq. (20) shows that the field falls off exponentially withdistance from the interface as shown in FIG. 17 once θ_(i)>θ_(c) wheretotal internal reflection takes place.

FIG. 17 shows for photon evanescent waves the same exponentiallydecaying behavior we saw in FIG. 11B for surface plasmons. All threewaveforms are evanescent photon evanescent waves, surface plasmons andsurface plasmon polaritons. Like “photon evanescent waves”, surfaceplasmons propagate along the interface they are created on. While photonevanescent waves extend on the order of ˜200 nm in the optical spectrum,they extend about 10⁵ times this value or ˜2 cm in the RF region ofX-band. Hecht, “Optics” 1^(st) Ed. 1979, Addison Wesley, pg. 84. Surfaceplasmon evanescent waves on the other hand may extend for meters.

For the illustrated embodiment, the RF coupling mechanism followsLockyear, et al., “Enhanced Microwave Transmission Through a SingleSubwavelength Aperture Surrounded by Concentric Grooves”, J. Opt. A.:Pure and Applied Optics, 1/05, S152-S158. It employs both a singlesubwavelength aperture for evanescent wave coupling to the other side ofa metal layer, and a two-sided surface grating for surface plasmonpolariton enhancement of the illuminated side while diffraction focusingon the exit (inside the radome). Circular apertures in an opaque metallayer of diameter:

$\begin{matrix}{d < {1.841\; \frac{\lambda}{\pi}}} & (24)\end{matrix}$

are unable to support propagating waveguide modes.

Thus, energy may only be transferred by the evanescent tunneling processleading to very weak transmission, which has been predicted to scale as(d/λ)². See H. A. Beth, “Theory of Diffraction by Small Holes”, ThePhysical Review, Vol. 66, N 7 & 8, Oct. 1 & 15, 1944, pg. 163-182,specifically pg. 171.) (Lockyear, supra, states the exponent is 4 whilethe original paper he references by Beth states an exponent of 2, andthus is used here.)

A cross section of a circular grating with surface spatial periodicityD, is shown in FIG. 18, where grating spacing is close to incidentradiation wavelength. The incident beam 1800 is diffracted producingpropagating modes in diffraction orders 1803, which travel away from theinterface while surface wave photon modes (photon evanescent waves)exist only at the interface, similar to those found at dielectricboundaries after total internal reflection. These modes have wave-vectorcomponents parallel to the interface with integer quanta of the gratingwave-vector added or subtracted, depending on the direction of thediffracted order. For a grating pitch of D the grating wave-number isk_(g)=2π/D, so the light wave-vector will be increased (or decreased) by2π/D (for the ±1^(st) order) and the dispersion relation of the surfaceplasmon component can be matched to that of a light wave-vector parallelto the interface (projection of lightwave k, i.e., k_(z)=k sin θ₀, whereθ₀ is the RF incident angle). Notice it is the incident light that seesa k-vector shift, not the plasmons.

By virtue of a grating, evanescent photon modes couple to surfaceplasmons (1906), which run along the interface between the grating andsupporting medium. The grating structure imposes an effective surfaceimpedance as seen by incident RF. In other words, like light entering adielectric, the light wavelength is changed permitting resonance withthe plasmons in a manner analogous to a dielectric impedance leveragedby the Otto (FIG. 13B) or Kretschmann-Raether (FIG. 13C) configurations.

For an incidence angle θ₀ and ε permittivity of the respective mediumsthe grating resonance condition takes the form:

$\begin{matrix}{k_{z} = {{{\frac{\omega}{c}\sin \; \theta_{o}} + \frac{2\pi}{D}} = {\frac{\omega}{c}\sqrt{\frac{ɛ\; 2}{{ɛ\; 2} + 1}}}}} & (25)\end{matrix}$

where ε2 is the permittivity of the metal assuming air as ε1=1. FIG.19A-FIG. 19B show a schematic representation of electric fields 1901,1903 associated with surface plasmon modes propagating along the surface1906, 1907 of a metal. At microwave frequencies, the metal is almostperfectly conducting, meaning in part, that the E-field vector at theair/metal interface is zero, i.e., the reflected transverse E-field ispointed opposite that of the incident transverse field vector at theinterface for a net zero field result in the metal (for perfectconductors).

In FIG. 19A the field 1900 is completely excluded from the metalsubstrate 1909 but extends for many wavelengths into the dielectricregion above making plasmons simply a surface current. In FIG. 19B thefield 1903 meets a “metamaterial” 1910, penetrating some depth thanks toperforating the substrate with an array of subwavelength apertures 1912(only one indicated). An elementary discussion of metamaterials is foundin Pendry, John B. & Smith, David R., “The Quest for the Superlens”,Scientific American, pp. 60-67 (July 2006), which is hereby incorporatedby reference for that discussion as if set forth verbatim herein.

Thus, in the illustrated embodiment, the subwavelength apertures 1003,shown in FIG. 10, cause the substrates to behave as if fabricated from ametamaterial. The apertures allow E-fields to decay exponentially intothe structure as evanescent waves, and they closely resemble those of asurface plasmon propagating on metals. Hibbins, et al., “ExperimentalVerification of Designer Surface Plasmons”, Science, Vol. 308, No. 5722,pg 670-672, 29 Apr. 2005. These decaying E-fields are the “evanescentwaves” discussed above. In the present case, the substrate 1015 isassumed to be far too thick to be penetrated. Instead, the evanescentwaves propagate only by the subwavelength apertures. The subwavelengthapertures 1003 in the metal substrate 1015 act as waveguides andtherefore have a cutoff frequency below which no propagating modes areallowed.

The classical cutoff designation of the cutoff frequency defines theboundary between a small aperture (not shown) and a subwavelengthaperture such as the apertures 1003 in FIG. 10. Below cutoff, onlyevanescent fields exist on the metal side of the air/metal interface.(Analogously, the incident field has been totally reflected at thesurface. Under such conditions exceeding the critical angle, evanescentwaves are established beyond dielectric barriers in the Otto (FIG. 13B)and Kretschmann-Raether (FIG. 13C) configurations. Here the incidentwaves arrive at normal incidence as tunneling is most efficient underthose conditions.)

For the current interest in 10 GHz X-band of freespace 3 cm wavelength,from Eq. (3), diameters less than d=1.76 cm (0.7″) cannot propagate. Fora dielectrically loaded guide with an index of refraction n=1.5 thewavelength becomes λ_(n)=2 cm and non-propagating d becomes 0.88 cm(0.35″). Table 1 and FIG. 20 survey subwavelength aperture diametersderived from Eq. (1.0) for four RF frequencies and a variety ofdielectric constants. Naturally, higher frequency and higher index ofrefraction yield smaller apertures occupying less radome space buthigher index also means greater reflection at the interface (more loss).

TABLE 1 Subwavelength Apertures v. Frequency & Index of Refraction X: 10GHz Ku: 20 GHz Ka: 35 GHz W: 95 GHz n = 1.5 11.7202 mm  5.8601 mm 3.3486mm 1.2337 mm n = 2.5 7.0321 mm 3.5161 mm 2.0092 mm 0.7402 mm n = 3.55.0229 mm 2.5115 mm 1.4351 mm 0.5287 mm n = 4.5 3.9067 mm 1.9534 mm1.1162 mm 0.4112 mm n = 5.5 3.1964 mm 1.5982 mm 0.9133 mm 0.3365 mm n =6.5 2.7047 mm 1.3523 mm 0.7728 mm 0.2847 mm n = 7.5 2.3440 mm 1.1720 mm0.6697 mm 0.2467 mm n = 8.5 2.0683 mm 1.0341 mm 0.5909 mm 0.2177 mm n =9.5 1.8506 mm 0.0009253 mm 0.5287 mm 0.1948 mm

Lockyear, supra, has gone far to clarify the phenomena associated withthis kind of transmission and provides information which makes the anglemethod used herein an enhancement to the NCFDF method, both phenomenausing an amplitude versus incident angle response which allows forcorrelation between amplitude and angle. Depending on how thesubwavelength aperture is placed, both methods can work together withthe same amplitude versus angle behavior, though by vastly differentmeans.

FIG. 21A-FIG. 21B provide Lockyear's design on a flat plate 2100 whichthe embodiment 1000 of FIG. 10 will, in part, emulate. The couplingmechanism of the embodiment 1000 in FIG. 10 is based on the concentric,or “bull's eye”, grating of Lockyear, and Lezec, et al., “Beaming Lightfrom a Subwavelength Aperture”, 297 Science 297, 820-822 (Aug. 2, 2002),before him. FIG. 21A shows the concentric circles 2103 (only oneindicated) of the bull's eye grating 2101 surrounding a subwavelengthaperture 2110 in a perspective view. FIG. 21B shows the aperture 2110and a ring 2103 in a fragmented cross-sectional view. Initialcomputational modeling demonstrated that the attenuation of thetransmitted signal through Lockyear's aperture 2110 was too high forsignal detection; hence, he countersunk the aperture 2110 driving thehole thickness toward zero at its metal boundary. This allows for asufficiently deep surface grating 2101 on both the illuminated and exitsides 2112, 2113 of the plate 2100 when the metal substrate thickness(h) is chosen to be 1.50 mm.

The grating pitch (or period or constant) was set to 5 mm, which waschosen because when the grating wave-number, k_(g)=2π/λ_(g) matches thatof the incident light then resonance is a maximum—thus the resonantfrequency used was 60 GHz. The aperture diameter is shown as 2.5 mm(half the illumination wavelength), material thickness of aluminum is1.5 mm, groove depth l is 0.55 mm, and width of groove is 1.5 mm. Alsoshown is a cross section through the structure on one side of the holeand the first grating peak as well as defining where is z=0.

Lockyear actually tested four surface patterns. The four surfaces usedby Lockyear to test are shown in FIG. 22A-FIG. 22D. FIG. 22A shows twosmooth surfaces 2200, 2201 with no corrugation on either side. FIG.22B-FIG. 22C have one sided corrugation allowing the corrugated sides2204, 2205 to face toward or away from the RF source. (The experimentrevealed very different phenomena of enhancement on the illuminated sideversus strong focusing on the exit side.) FIG. 22D shows corrugation onboth surfaces 2208, 2209. Source incident angle of θ and transmissionangle ψ are shown with respect the z-axis through the aperture 2110 areshown in FIG. 21. Light is E-polarized in the xz-plane.

FIG. 23A-FIG. 23D show how grooves of the grating 2101 were tuned. Withthe source frequency set to 60 GHz the E-field enhancement wasmonitored. FIG. 23A varies groove position, FIG. 23B varies groovedepth, FIG. 23C groove width and FIG. 23D the number of grooves. Thisthen results in an RF surface prescription for Lockyear's material andfrequency of choice noted above. Note that subsequent analysis wasconstrained to a plate 2100 with four concentric rings 2103 in order toimprove convergence and reduce computation time.

FIG. 24 illustrates Lockyear's test setup 2400, which is a good sourcefor the arrangement of the presently illustrated embodiment. Though thesource antenna 2403 appears fixed at normal incidence, it is later movedto three additional incident angles. Radiation is normally incident uponthe plate 2100 (θ=0°), and polarized such that the electric field vectorE is in the x-direction. The structures were milled into 300×300×1.5 mmaluminum alloy sheet, the edges of which were covered with microwaveabsorbing material 2409 to reduce stray signals.

The source antenna 2403 is positioned a perpendicular distance of 0.6 mfrom the sample plate 2100 and oriented such that the incident electricvector E is in the x-direction. The sample plate 2100 is mounted in awooden holder (not shown) and positioned over the center of rotation ofa computer-controlled turntable (not shown). A 45×45 mm aperture 2406formed from microwave absorbing material 2409 is positioned between thesource antenna 2403 and the plate 2100 to restrict the beam 2412 to awell collimated central part. A detector antenna 2415 is mounted on anarm (not shown) extending from the computer-controlled turntable andpositioned a perpendicular distance of 0.35 m from the exit side 2421 ofthe sample plate 2100.

In FIG. 25, the surface 2205 of FIG. 22C with corrugation facing thesource antenna 2403 is measured and modeled. Results are normalized tothe surface 2200 of FIG. 22A with no corrugations. Both transmit andreceive antennas 2403, 2415 are normal to their respective surfaces. Theillumination-side grating accounts for a 17-fold enhancement, or 12 dBover the bare aperture 2100 of FIG. 22A and its theoretical transmissionnoted by Beth, supra.

FIG. 26A-FIG. 26B shows that scattering of incident radiation by theconcentric grooves of the plate 2100 results in a redistribution of EMfields such that regions of high energy density are located in thevicinity of the aperture 2100. The E-field is shown in FIG. 26A topossess maxima located at sharp comers of each concentric groove, withmaximum enhancement (in this case 25-fold) occurring at the sharp ringformed by countersinking of the aperture entrance. The H-field, shown inFIG. 26B, however has maxima located centrally on each peak and troughof the profile. Note also that magnitudes of both E- and H-fields in thexz-plane decay as a function of distance away from the aperture(evanescent).

In FIG. 27 the surface wave is not concentric but dependent on incidentpolarization, implying that some embodiments need not have continuousrings although that would limit the polarization angle. With continuousrings, an embodiment would be polarization independent, accepting theE-field at an angle rotating about the aperture, though the RF-feedpickup would also have to be sensitive to any incoming polarization(circular).

Lockyear, supra, goes on to show a 16% enhancement clearly due tosurface plasmon polaritons because he models the aperture and grating onboth a perfect dielectric, perfect conductor, and aluminum. While thedielectric grating will still diffract, it cannot provide free electronsfor surface plasmon modes. The metal can and does display a gainresulting from surface plasmon polaritons. To summarize, Lockyear findsa pseudo-standing wave formed via diffraction, resulting in aredistribution of energy density such that regions of high energydensity are located in the vicinity of the aperture. Surface plasmonpolariton enhancement of the evanescent fields occurs for metals, butaccounts for less than a quarter of the overall enhancement intransmission in his study. Grating the illuminated surface providesenhancement while grating the inner surface focuses the incoming beam asshown in FIG. 28 below.

Lockyear notes that although the results of FIG. 28 suggest that plate2100 with a surface 2204 shown in FIG. 22B transmits more than plate2100 with surfaces 2200, 2201, shown in FIG. 22A, modeling of theabsolute transmission normalized to the area of the hole suggests theyare equally efficient. The apparent increase in transmission efficiencyis because Lockyear's detector antenna 2415, shown in FIG. 24, is onlyable to detect radiation entering close to normal to its front face.Further, diffraction of the beam 2412 occurs not only in the xz-planebut in all directions over a wide range of angles, as one would expectfor a circular hole and shown in FIG. 29A-FIG. 29B where absence of anexit grating (but presence of an illumination-side grating) results inwide beamwidths (FIG. 29A), while presence of an exit grating focusesthe beam 2412 (FIG. 29B). The inside grating forces the signal to exitthe aperture 2110 normal to the surface plane largely irrespective ofincident angle. See Lockyear, supra, p. S158.

Returning now to FIG. 10, the illustrated embodiment comprises asubwavelength aperture 1003 in a metal radome 1009, with illuminate andexit side concentric gratings 1008 and a dielectric medium 1012 encasingboth, filling the subwore aperture 1003 and extending into the radomevolume (not shown). Employing a subwavelength aperture 1003 allows anextended range of long wavelengths that may be passedevanescently—albeit with increasing loss—that a waveguide wouldotherwise reject if below its cutoff. The dielectric medium 1012 servesseveral purposes. First, it shortens the RF wavelength in dielectricmedium 1012 allowing us to reduce grating period which matches incidentwavelength in the dielectric medium 1012, and shrinks the subwavelengthaperture 1003, both satisfying limited radome real estate constraints.Second, it also serves to increase the number of grating groves,improving enhancement as described by Lockyear and shown in FIG. 23D.Third, it improves accuracy at the expense of reflection loss, onceagain, through the Fresnel operation employed by NCFDF as disclosed inthe '645 patent incorporated above.

Although one would rather not take the Fresnel loss, not only must spacerestrictions be satisfied but also constraints on subwavelengthapertures and their gratings prefer normal incidence RF or light. Onecannot provide this on such a strongly curved surface and still seeforward without the dielectric medium 1012, which translates a 20°freespace FOV into a dielectric transmitted ray varying by only 3° ontothe grating/aperture. While tolerances at optical wavelengths are strictas implied in FIG. 30A-FIG. 30C, such precision is relieved by a factorof wavelength increase over optical at RF wavelengths. FIG. 30A-FIG. 31Cshow the effect of grating period errors about a subwavelength apertureat optical wavelengths.

Note that these are implementation specific considerations for theillustrated embodiment. Alternative embodiments may balance these typesof constraints differently. For example, some embodiments may not havesuch tight size and shape constraints for their radome 1009.

Unlike hemispherical radiation, equal in amplitude in all directionsfrom each antenna element, the antenna of FIG. 10A-FIG. 10B primarilyprovides a steep amplitude versus angle variation per receiving elementprovided by the interaction between its subwavelength aperture andsurface grating as shown in FIG. 31A-FIG. 31B for the cases shown inFIG. 22D with gratings on both sides 2208-2309. Here the incident angleis varied over steps (0°, 10°, 20°, 30°) tracing out an effectivebeamwidth as roughly shown at right for the only values available fromthe plot in FIG. 31A.

Lockyear's tuning shown in FIG. 23A-FIG. 23D provides values for gratingstructures as shown in Table 2 (through scaling). Scaling the values toa 10 GHz freespace wavelength from Lockyear's 60 GHz yields a factor of0.5 cm/3 cm=6.0 shown in the 10 GHz freespace column. The same structurecomponents are shown also for several index of refraction values imposedon the dielectric layer. Note that per FIG. 23A-FIG. 23D, tolerances are±0.001 inch.

TABLE 2 Grating Structure Comparison 60 GHz 10 GHz Freespace 10 GHz, n =1.5 10 GHz, n = 3 Grating Pitch, λ_(g) 5 mm 30 mm 20 mm 10 mm GroveWidth, w 1.5 mm 9 mm 6 mm 3 mm Grove Depth, 1 0.55 mm 3.3 mm 2.2 mm 1.1mm Hole diameter, d 2.5 mm 15 mm 10 mm 5 mm Factor per 60 GHz 1 6 4 2 10GHz, n = 4.5 10 GHz, n = 5.5 10 GHz n = 6.5 10 GHz, n = 7.5 10 GHz, n =8.5 Grating Pitch, λ_(g) 6.7 mm 5.35 mm 4.62 mm 4 mm 3.53 mm GroveWidth, w 2 mm 1.64 mm 1.39 mm 1.2 mm 1.06 mm Grove Depth, 1 0.73 mm 0.6mm 0.51 mm 0.44 mm 0.39 mm Hole diameter, d 3.33 mm 2.73 mm 2.31 mm 2.0mm 1.77 mm Factor per 60 GHz 1.33 1.09 0.92 0.8 0.71

Notice a difference between values of Table 1 (based on Eq. (3)) andTable 2 based on scaling. For 10 GHz, index n=1.5 and n=3.0, Eq. (3)gives aperture d=11.7 mm and 5.86 mm respectively, both a 17.2%difference with Table 2 (using Table 2 values as the divisor). A tradebetween groove number, increased by elevated dielectric constant, itsassociated loss and decrease in NCFDF monopulse angle accuracy isrequired for each radome application and its RF frequency. FIG. 32 showsthe beneficial effects on groove surface spacing (radome real estate)versus dielectric constant for 10, 35 and 95 GHz.

FIG. 33 shows the detrimental effects of increasing index on what wouldbe both reflection loss (for higher index—i.e., greater impedancemismatch) and reduced magnitude versus angle slope independent offrequency, thus reducing track accuracy.

The illustrated embodiments therefore assist NCFDF monopulse angles byadding the change in amplitude versus angle of the subwavelengthaperture response to the NCFDF response. Though the illustratedembodiments provide a resonance phenomena, they create a patternanalogous to aperture beamwidth. Like classical monopulse antennas whichuse an amplitude versus angle relation as null seekers, it will make useof the resonance beamwidth for the same purpose. (This also means onecould angle-find with the present invention without the dielectric layer1012 and therefore without NCFDF.) One therefore chooses an angle atwhich to position the subwavelength aperture 1003 and grating 1008 atsome angle with respect to (and beneath) the dielectric medium 1012.

For current trajectories of interest for the illustrated embodiment, thetarget tends to be seen at 20° to 30° off boresight at launch. Thus, itis these angles at which the platform should see the farthest. By facingthe subwavelength aperture 1003 and grating 1008 in a manner such thatnormal subwavelength aperture incidence results from a ray refractedfrom a target one can tune detection range performance.

Slight variations in accuracy can be seen in the slopes of FIG. 34A-FIG.34C using the (“SRHIT”) factor of 0.33V/degree slope as equivalent to0.5 mrad track accuracy as shown in Table 3. Accuracy can be slightlyimproved if the subwavelength aperture peak amplitude (beam center) isdirected to 10° right of boresight (from the perspective of the leftside), i.e., place it at along the radome surface. However, thisarrangement incurs loss for all angles away from the nose—especially ofconcern at long range since simulations show large look angles at longrange for anticipated trajectories. Given the small accuracy improvementand desire for range performance aligning the subwavelength beam onboresight as shown in FIG. 34A is the compromise, though some designsmay choose otherwise.

TABLE 3 Accuracy Comparison FIG. 35A, Peak Forward FIG. 35B, Peak LeftFIG. 35C, Peak Right NCFDF Combined NCFDF Combined NCFDF Combined 1 mrad1 mrad 1 mrad 1.5 mrad 1 mrad 0.9 mrad

According to Beth, supra, radiation intensity falls off withsubwavelength aperture by (d/λ)². FIG. 35 shows the falloff of RF outputat X-band, Ka and W-bands versus index of refraction and variation indiameter over a range of values beginning at the max subwavelengthaperture limit of d=1.841λ/π of Eq. (1.0), decreasing to 1/20^(th) ofthis upper size limit. Note that λ is that within the dielectric medium.While tight surface space limitations are best suited by smallapertures, power behaves as always with more loss as the aperturesshrink.

Combining this loss with Fresnel loss, subwavelength beamwidth behaviorand illumination-side grating enhancement of 10 (Lockyear and othersapproach or exceed 100), one can calculate approximate received peakpower for the embodiment of FIG. 10 as shown in FIG. 36 where index andaperture have also been varied. The type of receiver used—RF orphotonic—will set noise floor and gains resulting in signal-to-noiseration (“SNR”) versus range performance.

Several other options and their combination are available to increaserange, including 1) increasing ground radar output power, 2) adding alow noise RF to the output of the RF-feed, and 3) combining the presentinvention with attenuated total reflection coupling for additionalplasmon amplification. Hence another purpose served by the dielectricmedium 1012 which fills a cavity behind the subwavelength aperture 1003,mated to a design attenuated total reflection coupling of a smooth thinmetal film with a rough surface or periodic structure on its far sideaway from the aperture facing an RF pick-up.

The present invention, in the embodiment of FIG. 10, therefore providesradar illuminator power rejection due to the near-normal incidence ofthe subwavelength aperture 1003 and gratings 1008. Physicalcharacteristics of subwavelength apertures present a series of tradeoffsas shown in Table 4.

TABLE 4 Subwavelength Tradeoffs Index Of Refraction High = smallfeatures, more gratings, more loss, lower accuracy Gratings More =greater signal enhancement, more surface space required SubwavelengthAperture Smaller = less surface space, greater coupling loss RadioFrequency Higher = smaller features, higher atmospheric loss, fewer3^(rd) party illuminator assets in the field, lower transmit power buthigher illuminator antenna gain

Thus, the embodiment of FIG. 10 presents another option for FOVrejecting, angle only measurement, addressing space limitations onminiature missiles with a surface conformal structure on sleek, low dragradomes, clearing the central axis for lethality. It is applicable toboth radio and optical regions of the electromagnetic spectrum andsuffers from the same monopulse centroid noise induced by multipath. Aswith all NCFDF-based devices, the accuracy is independent of aperturesize and wavelength as long as index of refraction is a constant. Alsoas with all NCFDF devices, lens foreshortening in the optical domainadds to accuracy at the expense of increased loss due to reducedaperture surface exposure to incoming light at the first interface wherethe NCFDF method is leveraged. While surface plasmon polaritons anddiffraction provide enhancement, photon tunneling (evanescent coupling)produces loss, dependant on aperture size.

Note that the technical discussion presented above relative to FIG.11A-FIG. 36 pertain to the embodiment of FIG. 10. However, as isdiscussed above, the present invention admits wide variation in manyaspects. For example, the grating 1008 may be implemented as shown inFIG. 5A-FIG. 5C or omitted altogether. Those ordinarily skilled in theart will be able to readily extrapolate from that discussion to make anduse numerous alternative embodiments.

Note also that the terminology used herein and in the claims below mayat times reflect the end use of a given embodiment. For instance, theinvention is employed at RF frequencies on a missile. Use at RFfrequencies mitigates for the use of the word “lens” over “window”,which might be used at optical frequencies, because the term “lens” areused in both RF and optical systems. However, in optical systems, the“lenses” 301, 302 of the radome 300, shown in FIG. 3A-FIG. 3B, may bereferred to as “windows” and the “lensing system” as a “windowingsystem”.

Similarly, both these factors mitigate for the use of the term “radome”although there is no need for a “radome”, as such, in all embodiments.The radome 300 performs several functions noted above in the illustratedembodiment. With respect to the present invention, however, the radome300 defines the geometry of the lenses 301, 302 with respect to theincident radiation. The geometry, in turn, impacts whether directionfinding can employ NCFDF in the given embodiment. Thus, any suitablemeans known to the art for defining that geometry may be employed giventhe implementation-specific constraint for a particular embodiment.Accordingly, the radome 300 is, by way of example and illustration, butone such determining means.

This concludes the detailed description. The particular embodimentsdisclosed above are illustrative only, as the invention may be modifiedand practiced in different but equivalent manners apparent to thoseskilled in the art having the benefit of the teachings herein.Furthermore, no limitations are intended to the details of constructionor design herein shown, other than as described in the claims below. Itis therefore evident that the particular embodiments disclosed above maybe altered or modified and all such variations are considered within thescope and spirit of the invention. Accordingly, the protection soughtherein is as set forth in the claims below.

1. A subwavelength electromagnetic wave receiver comprising: a lens,including: a dielectric medium; a substrate encased in the dielectricmedium and defining an subwavelength aperture; and a detector receivingenergy transmitted through the lens.
 2. The apparatus of claim 1,wherein the dielectric medium comprises a solid material or a fluidmaterial.
 3. The apparatus of claim 1, wherein the dielectric mediumcomprises fused silica, Duroid, plastic, diamond, or air.
 4. Theapparatus of claim 1, wherein the substrate comprises a metal or asemiconducting material.
 5. The apparatus of claim 1, wherein theaperture comprises an hourglass-shaped bore or a smooth bore.
 6. Theapparatus of claim 1, wherein the substrate includes a periodic surfacefeature functionally associated with the subwavelength aperture.
 7. Theapparatus of claim 6, wherein the periodic surface feature comprises agrating, a plurality of bumps, a plurality of posts, a plurality ofdivots, or a patch of roughness.
 8. The apparatus of claim 6, whereinthe periodic surface feature is a positive feature.
 9. The apparatus ofclaim 6, wherein the periodic surface feature is a negative surfacefeature.
 10. The apparatus of claim 1, wherein the detector comprises anoptical detector or a radio frequency detector.
 11. The apparatus ofclaim 1, further comprising a radome in which the lens is positioned.12. An apparatus comprising: a radome; an evanescent wave-coupledlensing system in the radome, including an opposed pair offorward-looking lenses, each lens comprising: a dielectric solid; and agrating defining a subwavelength aperture, the grating being encased bythe dielectric solid; and a detector capable of receiving energytransmitted through the lensing system.
 13. The apparatus of claim 12,wherein the missile radome comprises a metal or a dielectric material.14. The method of claim 12, wherein the lenses are foreshortened. 15.The method of claim 12, wherein the dielectric solid comprises fusedsilica, Duroid, plastic, or diamond.
 16. The method of claim 12, whereinthe grating comprises concentric geometric grooves, linear grooves, orarcuate grooves.
 17. The method of claim 12, wherein the gratingcomprises a metal or a semiconducting material.
 18. The method of claim12, wherein the aperture comprises an hourglass-shaped bore or a smoothbore.
 19. The method of claim 12, wherein the detector comprises anoptical detector or a radio frequency detector.
 20. The apparatus ofclaim 12, wherein the radome is a sleek radome.
 21. The apparatus ofclaim 12, wherein the sleek radome comprises a von Karman or an
 22. Theapparatus of claim 12, wherein the radome is a blunt radome.
 23. Theapparatus of claim 22, wherein the blunt radome comprises asemi-spherical or hemispherical radome.
 24. The apparatus of claim 12,further comprising means for performing a non-coherent fresnel directionfinding on the detected energy.
 25. A radio frequency antenna,comprising: a lensing system including a subwavelength aperture; meansfor defining the geometry of the lensing system and in which the lensingsystem is disposed; and a radio frequency detector capable of beingevanescent-wave coupled to the lensing system and detecting a radiofrequency signal received through the lensing system.
 26. The radiofrequency antenna of claim 25, wherein the determining means comprises aradome.
 27. The radio frequency antenna of claim 25, wherein the lensingsystem comprises a plurality of lenses or a collar.
 28. The radiofrequency antenna of claim 25, wherein the lensing system comprises: asubstrate defining the subwavelength aperture; and a dielectric mediumencasing the substrate.
 29. The radio frequency antenna of claim 28,wherein the substrate comprises a metal.
 30. The radio frequency antennaof claim 29, wherein the metal substrate defines a periodic surfacefeature on at least one of the illumination side and the exit sidethereof.
 31. The radio frequency antenna of claim 28, wherein thesubstrate comprises a semiconducting material.
 32. The radio frequencyantenna of claim 28, wherein the dielectric medium comprises at leastone of a composite material, a plastic, fused silica, diamond, and air.33. The radio frequency antenna of claim 28, wherein the substratedefines a plurality of subwavelength apertures.
 34. The radio frequencyantenna of claim 25, wherein the lensing system defines a plurality ofsubwavelength apertures.
 35. The radio frequency antenna of claim 25,wherein the metal substrate comprises a grating.
 36. The radio frequencyantenna of claim 25, wherein the cross-section of the aperture is anhourglass cross-section.
 37. The radio frequency antenna of claim 25,wherein the metallic substrate defines a plurality of subwavelengthapertures.
 38. An apparatus, comprising: a metal substrate defining asubwavelength aperture therein; and a dielectric solid encasing themetal substrate.
 39. The apparatus of claim 38, wherein thecross-section of the aperture is an hourglass cross-section.
 40. Theapparatus of claim 38, wherein the metal substrate comprises a grating.41. The apparatus of claim 40, wherein the grating includes concentriccircular grooves enclosing the aperture.
 42. The apparatus of claim 40,wherein the grating includes rectangular grooves.
 43. A method,comprising: receiving energy through a pair of opposing subwavelengthapertures; and determining a target angle from the steep change ofamplitude versus angle presented by the aperture's beamwidth.
 44. Themethod of claim 43, wherein the received energy is optical frequencyenergy.
 45. The method of claim 43, wherein the receive energy is radiofrequency energy.
 46. A lens, comprising: a substrate defining asubwavelength aperture therethrough and a periodic surface featurethereon; and a dielectric medium encasing the substrate.
 47. Anapparatus comprising: a sleek missile radome; a lensing system in themissile radome, including an opposed pair of forward-looking lenses,each lens comprising: a dielectric solid; and a grating defining asubwavelength aperture, the grating being encased by the dielectricsolid, the dielectric solid filling the aperture; and a detector capableof receiving energy transmitted through the lensing system.
 48. Theapparatus of claim 47, wherein the missile radome comprises a metal or adielectric material.
 49. The apparatus of claim 47, wherein the sleekradome comprises a von Karman or an Ogive radome.
 50. The apparatus ofclaim 47, wherein the lenses are foreshortened.
 51. The apparatus ofclaim 47, wherein the dielectric solid comprises fused silica, Duroid,plastic, or diamond.
 52. The apparatus of claim 47, wherein the gratingcomprises concentric geometric grooves, linear grooves, or arcuategrooves.
 53. The apparatus of claim 47, wherein the grating comprises ametal or a semiconducting material.
 54. The apparatus of claim 47,wherein the aperture comprises an hourglass-shaped bore or a smoothbore.
 55. The apparatus of claim 47, wherein the detector comprises anoptical detector or a radio frequency detector.
 56. A method,comprising: receiving an optical frequency signal through aforeshortened lens to which a non-reflective coating has been applied;and determining target angle from the received optical frequency signal.57. A method, comprising: receiving a returned radio frequency signalthrough a subwavelength aperture defined in a metal substrate underlyinga least a portion of a dielectric medium; and detecting the receivedsignal.
 58. An apparatus comprising: an opposing pair of antennas,separated by a predetermined distance, each antenna including: adielectric medium; a metal substrate defining subwavelength aperture,the grating being encased by the dielectric medium, the dielectricmedium filling the aperture; and a detector capable of receiving energytransmitted through the aperture.
 59. The apparatus of claim 58, whereinthe dielectric medium is a solid.
 60. The apparatus of claim 58, whereinthe metal substrate comprises a grating.
 61. A missile, comprising: asleek radome; a lensing system, including a pair of lenses, each lenscomprising: a dielectric medium; and a substrate encased in thedielectric medium and defining a subwavelength aperture therethrough anda periodic surface feature thereon; a pair of detectors, each detectorcapable of receiving energy transmitted through the lens; a flightcontrol mechanism; and a controller capable of non-coherent Fresneldirection finding a target from the received energy and transmitting aflight correction signal to the flight control mechanism responsivethereto.